A table (30) for an aircraft includes a table surface (56) deployable between a retracted position and a deployed position, an arm (50) having a first end and a second end, the arm (50) supporting the table (66) surface at the first end, a support connected to the arm (50) at the second end, the support connecting the arm to a structure interior to the aircraft, a sensor (136) within the aircraft to detect if a seat adjacent to the table surface is occupied, and a mechanism (120) for retracting the table surface to the retracted position if the sensor (136) detects at least one of that the seat is not occupied and that the aircraft flight mode meets predetermined criteria.
|
16. A method of operation of an exit row table for an aircraft comprising a table surface deployable between a retracted position and a deployed position, a sensor within the aircraft to detect if a seat adjacent to the table surface is occupied, a mechanism for retracting the table surface to the retracted position, the method comprising:
determining if predetermined flight conditions of the aircraft exist;
if the table surface is in the deployed position, automatically retracting the table surface to the retracted position upon determining that the predetermined flight conditions exist;
determining if the seat is occupied; and
if the table surface is in the deployed position, automatically retracting the table surface to the retracted position upon the sensor determining that the seat is not occupied.
1. A table for an aircraft, comprising:
a table surface deployable between a retracted position and a deployed position;
an arm having a first end and a second end, the arm supporting the table surface at the first end;
a support connected to the arm at the second end, the support connecting the arm to a structure interior to the aircraft;
a sensor within the aircraft to detect if a seat adjacent to the table surface is occupied; and
a retraction mechanism responsive to a signal provided by the sensor and to a flight mode of the aircraft meeting predetermined criteria, the retraction mechanism being configured to:
cause automatic retraction of the table surface to the retracted position upon the sensor detecting that the seat is not occupied and
cause automatic retraction of the table surface to the retracted position upon the aircraft flight mode meeting the predetermined criteria.
2. The exit row table of
3. The exit row table of
a locking mechanism for locking the table surface in a predetermined position between the retracted position and the deployed position if the sensor detects that the seat is occupied and if the aircraft flight mode does not meet the predetermined criteria that cause automatic retraction.
4. The exit row table of
5. The exit row table of
6. The exit row table of
a table support pivot disposed at the first end of the arm, permitting rotation of the table surface about the table support pivot.
7. The exit row table of
an arm pivot disposed at the second end of the arm, permitting rotation of the arm about the arm pivot.
8. The exit row table of
an extension disposed at the first end of the arm, permitting the table surface to be moved between the retracted position and the deployed position.
10. The exit row table of
13. The exit row table of
14. The exit row table of
15. The exit row table of
17. The method of
generating an unlock command if the seat is not occupied and if the predetermined flight conditions exist, wherein an unlock command unlocks the locking mechanism.
18. The method of
retracting the table surface in response to the unlock command.
19. The method of
a flight mode excluding taxi, takeoff, and landing.
20. The method of
a flight mode excluding an emergency condition.
|
This application is a national phase application under 35 U.S.C. 371 of International Patent Application No. PCT/IB2014/000637 filed on Apr. 29, 2014, which claims priority from U.S. provisional patent application No. 61/823,567 filed on May 15, 2013, the entire contents of which are hereby incorporated by reference.
The present invention concerns a construction for a table in an aircraft. Specifically, the present invention concerns a table in an aircraft that is contemplated to be positioned adjacent to an emergency exit, where the table includes features that facilitate egress from the aircraft in the event of an emergency. The present invention also is contemplated to be employed on a smaller aircraft such as a private aircraft or a corporate aircraft, particularly a jet aircraft.
Passenger seating adjacent to an emergency exit row presents unique engineering challenges when configuring the interior of an aircraft.
As should be apparent to any traveler, in the event of an emergency, it is necessary for the passenger to be provided with access to the emergency exit. This includes access to a doorway or to an emergency exit window. For purposes of the discussion that follows, the term “emergency exit location” is intended to refer to any point of egress from an aircraft, regardless of the mode of egress (i.e., a door or window).
Ensuring access to an emergency egress location may involve any of a number of different design parameters. For example, the aisle providing access to the emergency egress location may be wider than other aisles on board the aircraft.
Separately, it is known that some aircraft designers provide removable tables for passenger seats that are adjacent to an emergency exit location. The removable tables are intended to be separable from the passenger seat. In this design, any person who tries to access the emergency exit location may remove the table from the seat, thereby removing any obstruction that might discourage access to the emergency location.
As should be apparent to those skilled in the art, there are still further design alterations that may be made to assure access to emergency exit locations.
One deficiency that has been identified in the prior art lies in the fact that a side table is not easily provided to a passenger who is seated near to an emergency exit location.
It is in the context of this confluence of factors that the present invention was developed.
The present invention addresses one or more of the deficiencies noted with respect to the prior art.
In one contemplated embodiment, the present invention provides a table for an aircraft that includes a table surface deployable between a retracted position and a deployed position, an arm having a first end and a second end, the arm supporting the table surface at the first end, a support connected to the arm at the second end, the support connecting the arm to a structure interior to the aircraft, a sensor within the aircraft to detect if a seat adjacent to the table surface is occupied, and a mechanism for retracting the table surface to the retracted position if the sensor detects at least one of that the seat is not occupied and that the aircraft flight mode meets predetermined criteria.
It is contemplated that the mechanism may hold the table surface in a predetermined position if the seat is occupied and also, possibly, if the aircraft flight mode meets predetermined criteria.
It is also contemplated that the exit row table includes a locking mechanism for locking the table surface in a predetermined position between the retracted position and the deployed position if the sensor detects that the seat is occupied and the aircraft flight mode meets predetermined criteria.
The exit row table of the present invention is contemplated to include a table surface that includes at least a first leaf and a second leaf that pivotally connected to one another.
The exit row table of the present invention also may include a table support pivot disposed at the first end of the arm, permitting rotation of the table surface about the table support pivot.
It is also contemplated that the exit row table includes an arm pivot disposed at the second end of the arm, permitting rotation of the arm about the arm pivot.
In one embodiment, the exit row table of the present invention includes an extension disposed at the first end of the arm, permitting the table surface to be moved between the retracted position and the deployed position. The extension may be parallel to the arm. The extension may be disposed at an angle with respect to the arm.
The exit row table is contemplated to be stowable in a sideboard or an arm rest on the aircraft.
With respect to one or more embodiments of the exit row of the present invention, it is contemplated that the sensor is disposed in the seat and detects if a weight on the seat exceeds a predetermined amount.
The retraction mechanism may be at least one of a pneumatic damper, a hydraulic damper, a spring, and a servo motor.
The locking mechanism may be at least one of an electrical lock and a mechanical lock.
The aircraft flight mode is contemplated to exclude conditions associated with taxi, takeoff, and landing, among other flight conditions for which the exit table is recommended to be returned to the retracted position.
The present invention also is contemplated to encompass a method of operation of an exit row table for an aircraft that includes a table surface deployable between a retracted position and a deployed position, an arm having a first end and a second end, the arm supporting the table surface at the first end, a support connected to the arm at the second end, the support connecting the arm to a structure interior to the aircraft, a sensor within the aircraft to detect if a seat adjacent to the table surface is occupied, and a mechanism for retracting the table surface to the retracted position if the sensor detects at least one of that the seat is not occupied and that the aircraft flight mode meets predetermined criteria. The method is contemplated to include determining if predetermined flight conditions exist, determining if the seat is occupied, and retracting the table surface to the retracted position if the sensor detects at least one of that the seat is not occupied and that the aircraft flight mode meets predetermined criteria.
In another contemplated embodiment, where the exit row table further includes a locking mechanism for locking the table surface in a predetermined position between the retracted position and the deployed position if the sensor detects that the seat is occupied and the aircraft flight mode meets predetermined criteria, the method includes generating an unlock command if the seat is not occupied and predetermined flight conditions exist, wherein an unlock command unlocks the locking mechanism. With respect to this embodiment, the method also includes retracting the table surface in response to the unlock command.
The steps of determining if the seat is occupied are contemplated to be performed periodically.
The present invention also provides for an exit row table that includes a table surface deployable between a retracted position and a deployed position, an arm having a first end and a second end, the arm supporting the table surface at the first end, a scissor connected to the arm for deploying the arm and table surface between a first position to a second position, and a support connected to the arm at the second end, the support connecting the arm to a structure interior to the aircraft.
In this embodiment, the first position is contemplated to be within a compartment, such as a side ledge or armrest, and the second position is at least partially exterior to the compartment.
In another embodiment of the invention, it is contemplated that the exit row table will include an actuator connected to the scissor for applying a force on the arm to deploy the arm between the first position and the second position. As such, the scissor is contemplated to be responsive to a momentary application of a force to deploy the table surface between the first and second positions.
Further aspects of the present invention will be made apparent form the paragraphs that follow.
The present invention will now be described in connection with the drawing appended hereto, in which:
The present invention will now be described in connection with one or more embodiments thereof. The discussion of the embodiments is not intended to be limiting of the present invention. To the contrary, any discussion of embodiments is intended to exemplify the breadth and scope of the present invention. As should be apparent to those skilled in the art, variations and equivalents of the embodiment(s) described herein may be employed without departing from the scope of the present invention. Those variations and equivalents are intended to be encompassed by the scope of the present patent application.
The present invention will now be discussed in the content of the construction of a jet aircraft where one or more jet engines (also referred to as turbine engines or turbofan engines) are affixed (or attached) to each wing of the aircraft. While the invention is discussed in this context, the present invention is not intended to be limited solely to the construction of aircraft with wing-born jet engines. It is contemplated that the present invention may be employed in connection with any type of aircraft.
With respect to the discussion that follows, it is noted that specific directional conventions are assumed to be known to those skilled in the art. The directional conventions are consistent with the forward travel direction of the aircraft. In this context, the term “forward” (or its equivalent) refers to the front end (or bow end) of the aircraft. The term “rear” (or its equivalent) refers to the aft end (back end or stern) of the aircraft. The term “right side” (or its equivalent) refers to the right side (or starboard side) of the aircraft as defined by the forward and aft ends of the aircraft. The term “left side” (or its equivalent) refers to the left side (or port side) of the aircraft, also as defined by the fore and aft ends thereof.
Additionally, the term “longitudinal” refers to the longitudinal direction of the aircraft that extends from the front end to the rear end of the aircraft. The term “lateral” refers to the lateral direction of the aircraft that extends from the right side to the left side of the aircraft (i.e., as defined by the aircraft's wingspan). As should be apparent, the lateral direction is orthogonal to the longitudinal direction. The terms “up” (or top) and “down” (or bottom) refer to a vertical direction or orientation of the aircraft when the aircraft is parked on the ground.
In this illustration, it is noted that the passenger seat 32 is forward-facing and is disposed adjacent to a sideboard 34 extending along a port (or left side) section of the fuselage 12 of the aircraft 10. The exit row table 30 is connected to the sideboard 34 and extends from a mechanism (discussed in greater detail below) that is disposed within the sideboard 34. The exit row table 30 is contemplated to be stowable in the sideboard 34.
For reference, the passenger seat 32 includes a seat cushion 36, two arm rests 38, 40, a back rest 42, and a head rest 44. It is noted that these elements of the passenger seat 32 are merely illustrative of one embodiment of a passenger seat 32 that may be used in combination with the exit row table 30 of the present invention. Any alternative passenger seat 32 may be positioned within the aircraft 10 without departing from the scope of the present invention.
In addition, it is noted that a sideboard 34 is not required for stowage of the exit row table 30 according to the present invention. It is contemplated that the exit row table 30 may be stowed in a compartment in one of the armrests 38, 40 of the passenger seat 32 without departing from the scope of the present invention. In this regard, it is noted that the exit row table 30 is contemplated to be disposed in one of the armrests 38, 40 in the instance where the seat 32 is rotatable in its position within the aircraft 10.
The sideboard 34 includes an openable cover 46. The cover 46 is contemplated to tilt upwardly and toward the fuselage wall 48 of the aircraft 10, thereby permitting the passenger to access the interior of the sideboard 34 and deploy the exit row table 30 therefrom. As illustrated in
With continued reference to
As should be apparent to those skilled in the art, exit rows on an aircraft 10 are subject to particular regulations that, in summary, require the exit rows of the aircraft 10 to remain unobstructed during an emergency. As a result, any tables that are deployable in association with seats in exits rows are subjected to these additional requirements. These requirements limit the manner in which tables may be deployed in connection with such seats. As noted above, tables provided for seats in exit rows typically have limited adjustability so that they comply with applicable regulations and guidelines.
As will be made apparent in the discussion that follows,
In
The arm 50 is visible in
With continued reference to
In connection with the deployment of the exit row table 30 from the sideboard 34, it is contemplated that the exit row table 30 will be deployable after the cover 46 of the sideboard 34 is opened. After the cover 46 is opened, the passenger has access to the exit row table 30. To release the exit row table 30 from its stowed position, the passenger applies a downward pressure on the edge of the exit row table 30 (or other component) within the sideboard 34. The momentary push releases the exit row table 30, permitting a damper (or other suitable device) to push the exit row table 30 upwardly from the compartment within the sideboard 34 to a position that is more easily manipulated by the passenger.
The mechanism 68 includes a rail 72 that is connected to the bottom of the frame 70. The rail 72 is connected to the bottom of the frame 70 via a bracket 74. The rail 72 extends vertically from the bottom of the frame 70 to a position at or near the top of the frame 70. The rail 72 engages a slide 76 that slides along the rail 72. The rail 72 guides the slide 76 during its travel therealong.
The slide 76 connects to the support 66 via a support pivot 78. The support pivot 78 allows the support 66 to pivot from a vertical orientation (as shown) to a horizontal orientation, as shown in
At its bottom end, the slide 76 connects to the top end of a scissor jack 80. The bottom end of the scissor jack 80 connects to the rail 72. Depending upon the depth of the sideledge 34, it is contemplated that the bottom end of the scissor jack 80 may connect to the bottom end of the frame 70. Still further, it is contemplated that the scissor jack 80 may connect the slide 76 to any portion of the interior of the sideledge 34 without departing from the scope of the present invention.
As illustrated, the damper 82 connects between the slide 76 and the scissor jack 80. The damper 82 biases the scissor jack 80 to an opened position where the support 66 extends above the sideboard 34, exposing the support 66, the arm 52, and the table surface 56. As noted above, the damper 82 is designed to push the table surface 56 out from the sideledge 34 after being disengaged from a stowed position. When the passenger applies a momentary downward push onto the table surface 56, the arm 50, or the support 66, the damper 82 disengages from a stowed condition to push the table surface 56 upwardly, thereby exposing the table surface 56 from the compartment within the sideledge 34. This type of release mechanism is known to those skilled in the art and is, therefore, not discussed in greater detail herein.
As noted above, the support 66 is contemplated to slide vertically along the rail 72, together with the slide 76 to which the support 66 is pivotally attached. The slide 76 connects to the scissor jack 80 and the damper 82 such that, under the power of the damper 82, the slide 76 is pushed upwardly along the rail 72. As noted, after the passenger applies a momentary downward force on the mechanism 68, the mechanism 68 is released from a stowed condition within the sideledge 34.
Once the support 66 is exposed exterior to the sideledge 34, the arm 50 is rotated about the arm pivot 52 as illustrated in
In
In connection with the feature permitting the table surface 56 to be pushed away from the passenger, three embodiments are presented in connection with
As indicated in
So that the leading edge 98 of the table surface 56 does not remain within the boundaries 100, 102 during an emergency (or any other combination of predetermined flight conditions), the exit row table 84 is provided with a mechanism that facilitates automatic retraction of the exit row table 84 under certain conditions. The mechanism is discussed in greater detail in connection with
To facilitate this forward translation, the arm 50 is connected to an extension 108 that extends along the longitudinal direction of the aircraft 10. The extension 108 permits the table surface 56 to slide therealong, in the direction of the arrows 110. Alternatively, the extension 108 may slide with respect to the arm 50.
As in the previous embodiment, so that the leading edge 98 of the table surface 56 does not remain within the boundaries 100, 102 of the exit passageway 86 during an emergency, the exit row table 104 is provided with a mechanism that facilitates retraction, as discussed in greater detail in connection with
As with the previous two embodiments, so that the leading edge 98 of the table surface 56 does not remain within the boundaries 100, 102 of the exit passageway 86 during an emergency, the exit row table 112 is provided with an automatic retraction mechanism, which is described in greater detail in connection with
So that the arm 50 may be retracted during an emergency or under other preselected conditions, the pivot 52 includes a retraction mechanism 120. The retraction mechanism 120 biases the arm 50 so that the arm 50 moves, as a default, into the retracted position illustrated in
It is noted that the passenger in the passenger seat 32 may select a deployment position for the table surface 56 at any point between the fully retracted position and the fully deployed position. If the locking mechanism 122 is not activated, the table surface 56 will automatically default to the retracted position.
As noted above, one aspect of the present invention is to assure that the exit passageway 86 in front of the passenger seat 32 remains unobstructed, especially in the event of an emergency that would require access to the door 88. It is for this reason, among others, that the retraction mechanism 120 defaults to a retracted position unless the locking mechanism 122 is engaged. As discussed in greater detail with respect to
The retraction mechanism 120 may include any of a number of different devices for its operation. It is contemplated, for example, that the retraction mechanism 120 may be a pneumatic damper. Alternatively, the retraction mechanism 120 may be a hydraulic damper. Still further, it is contemplated that the retraction mechanism 120 may be a spring. The retraction mechanism 120 also may be a servo motor or a solenoid, as desired. As should be apparent from the foregoing, the exact construction and operation of the retraction mechanism 120 is not critical to the operation of the present invention.
Similarly, the locking mechanism 122 may be constructed in any of a number of different ways without departing from the scope of the present invention. The locking mechanism 122 may be an electrical switch, a mechanical switch, or an electro-mechanical switch, as should be apparent to those skilled in the art.
In addition, the exact position of the locking mechanism 122, while shown adjacent to the arm pivot 52, is not critical to the operation of the present invention. The locking mechanism 122 may be placed at any suitable location without departing from the scope of the present invention. While it is contemplated that the locking mechanism 122 will be located somewhere on the structure of the exit row table 84, the locking mechanism 122 may be positioned remotely (e.g., on the arm rest 38) without departing from the scope of the present invention.
As should be apparent for this embodiment of the exit row table 104, the arm 50 is not contemplated to pivot around the arm pivot 52. Instead, movement of the table surface 56 is made possible by the extension 108.
So that the table surface 56 may be retracted during an emergency or under other preselected conditions, the extension 108 includes a retraction mechanism 124. The retraction mechanism 124 in the illustrated embodiment is contemplated to be connected to the table support pivot 64, which slides along the extension 108. As in the prior embodiment, the retraction mechanism 124 is biased so that the table support pivot 64 (and, therefore, the table surface 56) is in the retracted position. As before, the retracted position is the default position that is illustrated in
It is noted that the passenger in the passenger seat 32 may select a deployment position for the table surface 56 at any point between the fully retracted position and the fully deployed position. If the locking mechanism 126 is not activated, the table surface 56 will automatically default to the retracted position.
As noted above, one aspect of the present invention is to assure that the exit passageway 86 in front of the passenger seat 32 remains unobstructed, especially in the event of an emergency that would require access to the door 88. It is for this reason, among others, that the retraction mechanism 124 defaults to a retracted position unless the locking mechanism 126 is engaged. As discussed in greater detail with respect to
The retraction mechanism 124 may include any of a number of different devices for its operation. It is contemplated, for example, that the retraction mechanism 124 may be a pneumatic damper. Alternatively, the retraction mechanism 124 may be a hydraulic damper. Still further, it is contemplated that the retraction mechanism 124 may be a spring. The retraction mechanism 124 also may be a servo motor or a solenoid, as desired. As should be apparent from the foregoing, the exact construction and operation of the retraction mechanism 124 is not critical to the operation of the present invention.
Similarly, the locking mechanism 126 may be constructed in any of a number of different ways without departing from the scope of the present invention. The locking mechanism 126 may be an electrical switch, a mechanical switch, or an electro-mechanical switch, as should be apparent to those skilled in the art. In another contemplated embodiment, it is contemplated that the locking mechanism 126 might be combined with the retraction mechanism 124. In other words, the present invention is not intended to be limited solely to embodiments where the retraction mechanism 124 and the locking mechanism 126 are elements that are separate from one another.
In addition, the exact position of the locking mechanism 126, while shown adjacent to the arm pivot 52, is not critical to the operation of the present invention. The locking mechanism 126 may be placed at any suitable location without departing from the scope of the present invention. While it is contemplated that the locking mechanism 126 will be located somewhere on the structure of the exit row table 104, the locking mechanism 126 may be positioned remotely (e.g., on the arm rest 38) without departing from the scope of the present invention.
So that the table surface 56 may be retracted during an emergency or under other preselected conditions, the extension 114 includes a retraction mechanism 128. The retraction mechanism 128 in the illustrated embodiment is contemplated to be connected to the table support pivot 64, which slides along the extension 114. As in the prior embodiment, the retraction mechanism 128 is biased so that the table support pivot 64 (and, therefore, the table surface 56) is in the retracted position. As before, the retracted position is the default position that is illustrated in
It is noted that the passenger in the passenger seat 32 may select a deployment position for the table surface 56 at any point between the fully retracted position and the fully deployed position. If the locking mechanism 130 is not activated, the table surface 56 will automatically default to the retracted position.
As noted above, one aspect of the present invention is to assure that the exit passageway 86 in front of the passenger seat 32 remains unobstructed, especially in the event of an emergency that would require access to the door 88. It is for this reason, among others, that the retraction mechanism 128 defaults to a retracted position unless the locking mechanism 130 is engaged. As discussed in greater detail with respect to
The retraction mechanism 128 may include any of a number of different devices for its operation. It is contemplated, for example, that the retraction mechanism 128 may be a pneumatic damper. Alternatively, the retraction mechanism 128 may be a hydraulic damper. Still further, it is contemplated that the retraction mechanism 128 may be a spring. The retraction mechanism 128 also may be a servo motor or a solenoid, as desired. As should be apparent from the foregoing, the exact construction and operation of the retraction mechanism 128 is not critical to the operation of the present invention.
Similarly, the locking mechanism 130 may be constructed in any of a number of different ways without departing from the scope of the present invention. The locking mechanism 130 may be an electrical switch, a mechanical switch, or an electro-mechanical switch, as should be apparent to those skilled in the art.
In addition, the exact position of the locking mechanism 130, while shown adjacent to the arm pivot 52, is not critical to the operation of the present invention. The locking mechanism 130 may be placed at any suitable location without departing from the scope of the present invention. While it is contemplated that the locking mechanism 130 will be located somewhere on the structure of the exit row table 112, the locking mechanism 130 may be positioned remotely (e.g., on the arm rest 38) without departing from the scope of the present invention.
In connection with the embodiments described in connection with
A seat sensor 136 is disposed in the seat 32, for example within the seat cushion 36, and is operatively connected to the retraction mechanism 120 associated with the exit row table 84. The seat sensor 136 is contemplated to be a weight sensor that detects if a sufficiently large amount of weight is present in the seat 32. If the weight on the seat 32 exceeds a predetermined amount, the seat sensor 136 provides a signal to the retraction mechanism 120 or the locking mechanism 122 to permit locking of the table surface 56 in a preselected position.
It is noted that the seat sensor 136 need not be a weight sensor. It is contemplated that the seat sensor 136 may include one or more sensors that operate independently or together with one another to measure parameters indicative of a person being seated in the passenger seat 32. Weight is only one variable that may be detected.
As for the first condition, as noted above, a seat sensor 136 is provided in the passenger seat 32. The seat sensor 136 is contemplated to sense if a sufficient amount of weight is present on the seat. In other words, the seat sensor 136 provides a weight signal. If the weight signal exceeds a predetermined minimum, then the first condition is satisfied.
The second condition may be satisfied by any of a number of different inputs that are available on board the aircraft 10. It is contemplated that the second condition is satisfied when the aircraft is not in a taxi, takeoff, and landing (“TTL”) mode of operation. During flight, it is contemplated that the second condition is satisfied when the aircraft 10 is not experiencing turbulence or other conditions where retraction of the table surface 56 is desirable.
In the discussion that follows, it is contemplated that the first condition is satisfied when a weight in excess of a predetermine amount is present in the seat 32. The second condition is considered to be satisfied when the aircraft is not in a TTL mode of operation.
The method 138 begins at step 140 where the method 138 enquires if predetermined conditions exist on board the aircraft 10. Specifically, the method 138 determines if the aircraft 10 is in a flight mode of operation (i.e., a non-TTL mode of operation). If the method 138 determines that predetermined conditions exist and that the aircraft 10 is not in a TTL mode of operation, then the method 138 proceeds to step 142. If the method 138 determines that predetermined conditions do not exist, this means that the aircraft 10 is no longer in a flight mode and that the aircraft 10 is preparing for taxi, takeoff, and landing. As a result, the method 138 proceeds to step 146 where an unlocking command is generated. The unlocking command causes the exit row table 30, 84, 104, 112 to return to the retracted condition.
After determining that predetermined conditions exist on the aircraft 10 suitable for deployment of the exit row table 30, 84, 104, 112, the method 138 proceeds to step 144, where the method 138 determines if the seat 32 is occupied. If the seat is occupied, the method 138 proceeds to step 144 where locking of the exit row table 30, 84, 104, 112 in a deployed condition is permitted. If the seat 32 is not occupied, the method 138 proceeds to step 146, where the unlocking command is generated.
As should be apparent, when the unlocking command is generated at step 146, the method proceeds to step 148 where the table surface 56 is retracted. If the table surface 56 is not deployed, then retraction of the table surface 56 is not necessary, since the table surface 56 automatically biases to the retracted condition, as discussed above.
With continued reference to
Similarly, the entirety of the method 138 may be executed periodically for the same reason. As such, if the conditions on board the aircraft 10 change, the exit row table 30, 84, 104, 112 will be retracted.
In operation, the exit row table 150 is contemplated to function as follows. When a passenger is seated in the seat 32 and actuates the seat sensor 136, the holding and retraction mechanism 152 permits the passenger to position the table surface 56 in any suitable location. The table surface 56, however, is not locked in the position. Instead, the table surface 56 is maintained in the position selected by the passenger. In this embodiment, it is contemplated that the table surface 56 is freely movable to any position between a retracted position and a deployed position without locking the table in a fixed position. Any suitable mechanism, as should be apparent to those skilled in the art may be employed without departing from the scope of the present invention.
When the passenger gets up from the seat 32 and, thereby alters the input to the seat sensor 136, it is contemplated in one embodiment that the holding and retraction mechanism 152 will retract the table surface 56 to a retracted position. Alternatively, if the flight conditions of the aircraft 10 require that the table surface 56 be in a retracted position, the holding and retraction mechanism 152 will retract the table surface 56 to the retracted position and prevent positioning of the table surface at any position between the retracted position and the deployed position.
As illustrated, the method 154 starts at a step 156 where the method determines if predetermined flight conditions exist. As noted above, the predetermined conditions include conditions where the aircraft 10 is not in a TTL mode of operation or experiencing turbulence, for example. The method 154 proceeds to step 158, where the method 154 determines if the seat 32 is occupied. If so, the table surface may be positioned in accordance with step 160. If the seat is not occupied, the method 154 proceeds to step 162, where the table surface 56 is retracted. In one alternative embodiment, if the predetermined conditions for the flying of the aircraft 10 do not exist (i.e., the aircraft 10 is in a TTL mode of operation), the table surface 56 is retracted as indicated in step 162. In yet another alternative embodiment, it is contemplated that the table surface 56 will remain in the deployed position even if the seat 32 is not occupied but the aircraft 10 is operating such that the predetermined flight conditions do not exist (i.e., the aircraft 10 is in a TTL mode of operation). In all other aspects, the method 154 is considered to be similar to the method 138 as described above.
A should be apparent from the foregoing, it is contemplated that there are two conditions that affect the whether or not the table surface 56 is retracted or deployable. The first condition is the flight condition of the aircraft 10. The second is the occupancy of the seat 32, as measured by the seat sensor 136. Either one or both of these conditions may have an impact on the deployability of the table surface 56. For example, if the aircraft 10 is in a flight mode excluding a TTL mode of operation, for example, this means that the aircraft 10 is in a condition where the table surface 56 may be deployed. It is contemplated, in one mode of operation, that the table surface 56 is deployable when the seat 32 is unoccupied and predetermined flight conditions are met. In a second contemplated mode of operation, the seat 32 must be occupied and the aircraft 10 must meet the predetermined flight criteria for the table surface 56 to be deployable.
While the exit row tables 30, 84, 104, 112, 150 have been discussed in connection with an embodiment for a seat 32 adjacent to an exit passageway 86, it is noted that the exit row tables 30, 84, 104, 112, 150 of the present invention may be used at any location within the aircraft without departing from the scope of the present invention. In other words, the exit row tables 30, 84, 104, 112, 150 may be employed in any location, as should be apparent to those skilled in the art.
As noted above, the embodiment(s) described herein are intended to be exemplary of the wide breadth of the present invention. Variations and equivalents of the described embodiment(s) are intended to be encompassed by the present invention, as if described herein.
Gagnon, Pierre, Huber, Stefan, Deka, Tom, Monardo, Michele, Roy, Jordan, Mageau, Christian, Haselberger, Christoph
Patent | Priority | Assignee | Title |
10106260, | May 15 2013 | Bombardier, Inc. | Exit row table for an aircraft |
10342338, | Mar 29 2017 | B/E Aerospce, Inc. | Stowage module mounted tray table with multi-bar linkage driven movement |
10351036, | Mar 30 2017 | B/E Aerospace, Inc. | Stowage module mounted tray table with arced deployment motion |
10370107, | Mar 31 2017 | B/E Aerospace, Inc. | Arced rail for aircraft tray table |
10889377, | Jun 28 2019 | B/E Aerospace, Inc. | Braking aircraft table system |
10926880, | Aug 28 2018 | Rockwell Collins, Inc.; Rockwell Collins, Inc | Timed passenger tray with infinite position |
11273747, | Nov 02 2020 | Ford Global Technologies, LLC | Multi-positional tray deployable from instrument panel |
11400844, | Jul 18 2018 | INTEVA PRODUCTS, LLC | Deployable table for vehicle interior |
11433795, | Jul 18 2018 | INTEVA PRODUCTS, LLC | Deployable table for vehicle interior |
9988149, | Feb 04 2015 | DASSAULT AVIATION | Interior layout assembly of an aircraft cabin, and related method |
Patent | Priority | Assignee | Title |
3583760, | |||
3632161, | |||
4834449, | Apr 18 1988 | Collapsible table assembly | |
4944552, | Mar 17 1989 | WEBER AIRCRAFT, INC , A CORP OF NEW JERSEY | Stowable table system |
5547247, | Aug 16 1994 | BE AEROSPACE, INC | Passenger tray table with ingress/egress position |
6273502, | May 25 2000 | Ergonomically designed chair with adjustable keypad support arrangement | |
6347590, | Feb 27 1999 | Lear Corporation | Center console stored extensible tray table |
6598934, | Feb 09 1999 | Johnson Controls Technology Company | Vehicle seat armrest mounted tray table |
7306282, | May 31 2000 | RECARO AIRCRAFT SEATING GMBH & CO | Table unit |
7311354, | Apr 30 2003 | 3861589 CANADA INC | Seat for aircraft |
7506923, | Apr 10 2008 | BE Aerospace, Inc. | Adjustable bi-fold tray table |
7798072, | Mar 31 2005 | Becker Automotive Design, Inc. | Stowable table assembly with a tabletop locking mechanism |
7874614, | Feb 03 2006 | FIGUERAS INTERNATIONAL SEATING, S A | System for mounting writing tablets to armchairs |
8033229, | Jul 07 2008 | Adjustable video and still image projector stand | |
8065966, | Sep 24 2009 | Bauer Products, Inc. | Odd link work surface lift |
8132518, | May 11 2007 | Siemens Medical Solutions USA, Inc. | Substantially linear vertical lift system |
8267472, | May 11 2007 | Thales | Seat provided with a pivoting display screen |
8276525, | Apr 08 2008 | Height-adjustable equipment stand | |
8448581, | May 24 2007 | J Thompson Solutions Ltd | Table apparatus for a vehicle seat |
8596206, | Jan 03 2011 | Safran Seats | Tray table assembly |
8672400, | Jun 10 2011 | Foldable table | |
20030154890, | |||
20070132283, | |||
20150289641, | |||
EP2213503, |
Executed on | Assignor | Assignee | Conveyance | Frame | Reel | Doc |
Jun 14 2013 | GAGNON, PIERRE | Bombardier Inc | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 038794 | /0811 | |
Jun 14 2013 | ROY, JORDAN | Bombardier Inc | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 038794 | /0811 | |
Jun 14 2013 | MONARDO, MICHELE | Bombardier Inc | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 038794 | /0811 | |
Jun 17 2013 | MAGEAU, CHRISTIAN | Bombardier Inc | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 038794 | /0811 | |
Jun 18 2013 | DEKA, TOM | Bombardier Inc | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 038794 | /0811 | |
Apr 29 2014 | Bombardier Inc. | (assignment on the face of the patent) | / | |||
Jan 29 2015 | HUBER, STEFAN | Bombardier Inc | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 038794 | /0811 | |
Jan 29 2015 | HASELBERGER, CHRISTOPH | Bombardier Inc | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 038794 | /0811 |
Date | Maintenance Fee Events |
Mar 31 2021 | M1551: Payment of Maintenance Fee, 4th Year, Large Entity. |
Date | Maintenance Schedule |
Oct 10 2020 | 4 years fee payment window open |
Apr 10 2021 | 6 months grace period start (w surcharge) |
Oct 10 2021 | patent expiry (for year 4) |
Oct 10 2023 | 2 years to revive unintentionally abandoned end. (for year 4) |
Oct 10 2024 | 8 years fee payment window open |
Apr 10 2025 | 6 months grace period start (w surcharge) |
Oct 10 2025 | patent expiry (for year 8) |
Oct 10 2027 | 2 years to revive unintentionally abandoned end. (for year 8) |
Oct 10 2028 | 12 years fee payment window open |
Apr 10 2029 | 6 months grace period start (w surcharge) |
Oct 10 2029 | patent expiry (for year 12) |
Oct 10 2031 | 2 years to revive unintentionally abandoned end. (for year 12) |